FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 200,000 Max Cl/Cd: 70.86 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61163-il-200000.txt Download as CSV file: xf-fx61163-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2875 0.10693 0.10379 -0.0507 1.0001 0.0544
-11.500 -0.3082 0.10006 0.09696 -0.0556 1.0001 0.0549
-11.250 -0.3298 0.09282 0.08973 -0.0601 1.0001 0.0550
-11.000 -0.3123 0.09061 0.08761 -0.0556 1.0001 0.0568
-10.750 -0.3030 0.08888 0.08592 -0.0540 1.0001 0.0582
-10.500 -0.3046 0.08517 0.08225 -0.0543 1.0001 0.0595
-10.250 -0.3133 0.08009 0.07722 -0.0558 1.0001 0.0610
-10.000 -0.3366 0.07212 0.06930 -0.0597 1.0001 0.0616
-9.750 -0.3732 0.06423 0.06141 -0.0634 1.0001 0.0608
-7.750 -0.4018 0.03226 0.02583 -0.0917 0.8851 0.0335
-7.500 -0.3668 0.03038 0.02356 -0.0935 0.8629 0.0332
-7.250 -0.3382 0.02673 0.01968 -0.0938 0.8453 0.0314
-7.000 -0.3115 0.02459 0.01724 -0.0933 0.8297 0.0304
-6.750 -0.2858 0.02302 0.01543 -0.0925 0.8163 0.0299
-6.500 -0.2607 0.02180 0.01404 -0.0915 0.8049 0.0300
-6.250 -0.2360 0.02080 0.01291 -0.0905 0.7953 0.0305
-6.000 -0.2128 0.01995 0.01199 -0.0895 0.7855 0.0315
-5.750 -0.1892 0.01924 0.01119 -0.0889 0.7770 0.0326
-5.500 -0.1686 0.01806 0.00998 -0.0886 0.7693 0.0356
-5.250 -0.1439 0.01741 0.00929 -0.0889 0.7624 0.0409
-5.000 -0.1188 0.01643 0.00822 -0.0896 0.7556 0.0493
-4.750 -0.0917 0.01251 0.00657 -0.0949 0.7497 0.5062
-4.500 -0.0657 0.01317 0.00740 -0.0935 0.7431 0.5866
-4.250 -0.0409 0.01456 0.00872 -0.0911 0.7380 0.6227
-4.000 -0.0185 0.01600 0.01013 -0.0881 0.7326 0.6435
-3.750 0.0042 0.01712 0.01121 -0.0853 0.7271 0.6572
-3.500 0.0239 0.01824 0.01228 -0.0813 0.7226 0.6623
-3.250 0.0521 0.01835 0.01227 -0.0817 0.7175 0.6727
-3.000 0.0760 0.01860 0.01245 -0.0802 0.7125 0.6754
-2.750 0.1028 0.01871 0.01244 -0.0798 0.7082 0.6794
-2.500 0.1343 0.01847 0.01205 -0.0817 0.7038 0.6876
-2.250 0.1578 0.01864 0.01220 -0.0803 0.6989 0.6902
-2.000 0.1839 0.01874 0.01222 -0.0798 0.6948 0.6944
-1.750 0.2171 0.01857 0.01187 -0.0819 0.6911 0.7022
-1.500 0.2400 0.01866 0.01198 -0.0806 0.6862 0.7046
-1.250 0.2657 0.01871 0.01199 -0.0801 0.6816 0.7082
-1.000 0.2985 0.01857 0.01171 -0.0820 0.6776 0.7150
-0.750 0.3241 0.01858 0.01171 -0.0816 0.6731 0.7184
-0.500 0.3484 0.01864 0.01177 -0.0808 0.6681 0.7214
-0.250 0.3767 0.01863 0.01169 -0.0812 0.6640 0.7256
0.000 0.4112 0.01852 0.01146 -0.0835 0.6604 0.7316
0.250 0.4340 0.01857 0.01157 -0.0825 0.6555 0.7339
0.500 0.4601 0.01859 0.01159 -0.0822 0.6510 0.7369
0.750 0.4899 0.01859 0.01152 -0.0830 0.6473 0.7411
1.000 0.5228 0.01855 0.01145 -0.0850 0.6427 0.7463
1.250 0.5466 0.01857 0.01153 -0.0842 0.6377 0.7484
1.500 0.5732 0.01859 0.01152 -0.0839 0.6334 0.7514
1.750 0.6019 0.01864 0.01155 -0.0844 0.6289 0.7552
2.000 0.6343 0.01861 0.01155 -0.0863 0.6230 0.7599
2.250 0.6608 0.01860 0.01153 -0.0861 0.6186 0.7625
2.500 0.6872 0.01868 0.01160 -0.0858 0.6147 0.7652
2.750 0.7126 0.01875 0.01178 -0.0857 0.6088 0.7684
3.000 0.7437 0.01874 0.01176 -0.0868 0.6040 0.7721
3.250 0.7772 0.01878 0.01174 -0.0885 0.5998 0.7759
3.500 0.7992 0.01885 0.01195 -0.0875 0.5935 0.7783
3.750 0.8267 0.01884 0.01197 -0.0875 0.5885 0.7809
4.000 0.8554 0.01888 0.01202 -0.0880 0.5832 0.7839
4.250 0.8845 0.01889 0.01211 -0.0888 0.5762 0.7876
4.500 0.9172 0.01885 0.01205 -0.0901 0.5714 0.7908
4.750 0.9402 0.01894 0.01228 -0.0893 0.5648 0.7931
5.000 0.9675 0.01889 0.01227 -0.0894 0.5587 0.7956
5.250 0.9951 0.01887 0.01231 -0.0895 0.5518 0.7986
5.500 1.0243 0.01881 0.01231 -0.0901 0.5444 0.8020
5.750 1.0553 0.01880 0.01234 -0.0912 0.5375 0.8051
6.000 1.0798 0.01869 0.01233 -0.0906 0.5294 0.8073
6.250 1.1050 0.01863 0.01235 -0.0902 0.5214 0.8100
6.500 1.1320 0.01855 0.01234 -0.0902 0.5135 0.8131
6.750 1.1585 0.01851 0.01240 -0.0903 0.5035 0.8162
7.000 1.1877 0.01838 0.01232 -0.0909 0.4926 0.8192
7.250 1.2118 0.01825 0.01223 -0.0902 0.4824 0.8217
7.500 1.2341 0.01828 0.01241 -0.0894 0.4708 0.8245
7.750 1.2581 0.01833 0.01257 -0.0889 0.4590 0.8273
8.000 1.2830 0.01844 0.01274 -0.0887 0.4467 0.8303
8.250 1.3080 0.01858 0.01296 -0.0887 0.4318 0.8336
8.500 1.3279 0.01874 0.01316 -0.0875 0.4152 0.8363
8.750 1.3459 0.01900 0.01342 -0.0860 0.3962 0.8390
9.000 1.3629 0.01938 0.01383 -0.0846 0.3748 0.8419
9.250 1.3785 0.01991 0.01433 -0.0830 0.3521 0.8452
9.750 1.3998 0.02126 0.01568 -0.0786 0.3036 0.8518
10.000 1.4020 0.02223 0.01658 -0.0752 0.2774 0.8551
10.250 1.4046 0.02351 0.01779 -0.0725 0.2481 0.8587
10.500 1.4043 0.02519 0.01936 -0.0700 0.2204 0.8626
10.750 1.4018 0.02699 0.02112 -0.0675 0.1953 0.8663
11.000 1.3978 0.02917 0.02325 -0.0654 0.1750 0.8704
11.250 1.3960 0.03157 0.02564 -0.0642 0.1553 0.8747
11.500 1.3924 0.03436 0.02838 -0.0634 0.1374 0.8787
11.750 1.3875 0.03717 0.03119 -0.0623 0.1212 0.8826
12.000 1.3833 0.04013 0.03415 -0.0616 0.1051 0.8872
12.250 1.3782 0.04336 0.03736 -0.0612 0.0907 0.8920
12.500 1.3712 0.04651 0.04052 -0.0604 0.0790 0.8971
12.750 1.3640 0.04985 0.04389 -0.0598 0.0690 0.9030
13.000 1.3548 0.05341 0.04745 -0.0592 0.0611 0.9091
13.250 1.3490 0.05656 0.05069 -0.0586 0.0542 0.9164
13.500 1.3376 0.06041 0.05455 -0.0581 0.0491 0.9248
13.750 1.3346 0.06310 0.05740 -0.0573 0.0434 0.9392
14.000 1.3223 0.06648 0.06083 -0.0564 0.0397 0.9999
14.250 1.3205 0.07039 0.06482 -0.0575 0.0337 0.9999
14.500 1.3101 0.07540 0.06982 -0.0588 0.0291 0.9999
14.750 1.3040 0.07999 0.07450 -0.0600 0.0249 0.9999
15.000 1.2889 0.08569 0.08022 -0.0614 0.0223 0.9999
15.250 1.2857 0.08997 0.08463 -0.0626 0.0199 0.9999
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